GB1264637A - - Google Patents

Info

Publication number
GB1264637A
GB1264637A GB1264637DA GB1264637A GB 1264637 A GB1264637 A GB 1264637A GB 1264637D A GB1264637D A GB 1264637DA GB 1264637 A GB1264637 A GB 1264637A
Authority
GB
United Kingdom
Prior art keywords
rotor
vibrations
plane
support member
pendulous
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed filed Critical
Publication of GB1264637A publication Critical patent/GB1264637A/en
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/001—Vibration damping devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
    • F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
    • F16F15/10—Suppression of vibrations in rotating systems by making use of members moving with the system
    • F16F15/14—Suppression of vibrations in rotating systems by making use of members moving with the system using masses freely rotating with the system, i.e. uninvolved in transmitting driveline torque, e.g. rotative dynamic dampers
    • F16F15/1407—Suppression of vibrations in rotating systems by making use of members moving with the system using masses freely rotating with the system, i.e. uninvolved in transmitting driveline torque, e.g. rotative dynamic dampers the rotation being limited with respect to the driving means
    • F16F15/145—Masses mounted with play with respect to driving means thus enabling free movement over a limited range
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/50—Vibration damping features

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Acoustics & Sound (AREA)
  • Vibration Prevention Devices (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

1,264,637. Damping vibrations in helicopter rotors. UNITED AIRCRAFT CORP. 16 July, 1969 [20 Sept., 1968], No. 35711/69. Heading B7W. [Also in Division F2] Vibrations in the plane of rotation of a helicopter rotor 60, Fig. 6, are damped by the presence of at least three "bifilar vibration dampers " 80 connected to the rotor for rotation therewith and oriented in a plane parallel to the plane of rotation. Each " bifilar vibration damper " 80, Fig. 7, can be tuned (by altering its geometry) to any particular vibration, and comprises a pendulous member 86 located at the extremity of a support member 70 which is connected to the rotor hub assembly; the member 80 includes side plates 92, 94 having circular apertures 98, 100 therein which are substantially the same diameter as corresponding apertures 82 in the support member 70. A pin 90 extends through apertures 98, 82, 100 and serves to connect the pendulous member to the support member in rolling fashion. Annular spacer members 116, 118 positioned as shown are dimensioned to be thickest adjacent the pin and to taper outwardly therefrom so that there obtains only line contact between the relatively moving parts. In operation the various components adopt the configuration of Figs. 8, 12 (not shown). The pendulous members may be supported directly from the rotor hub assembly, or they may be used in a rotor propelled by tip jets, Figs. 10, 11 (not shown). The bifilar vibration dampers may be positioned, oriented and tuned to absorb rotor vibrations in any plane, if desired, and it is stated that they can be adapted to damp vibrations in all six degrees of freedom.
GB1264637D 1968-09-20 1969-07-16 Expired GB1264637A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US76118768A 1968-09-20 1968-09-20

Publications (1)

Publication Number Publication Date
GB1264637A true GB1264637A (en) 1972-02-23

Family

ID=25061434

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1264637D Expired GB1264637A (en) 1968-09-20 1969-07-16

Country Status (5)

Country Link
US (1) US3540809A (en)
DE (1) DE1940770C3 (en)
FR (1) FR2018491B1 (en)
GB (1) GB1264637A (en)
SE (1) SE352586B (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4550812A (en) * 1978-08-04 1985-11-05 United Technologies Corporation Fixed position, fixed frequency pendular-type vibration absorber with frequency linearization

Families Citing this family (37)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1443148A (en) * 1972-10-19 1976-07-21 Westland Aircraft Ltd Bifilar vibration dampers
GB1445686A (en) * 1972-11-06 1976-08-11 Westland Aircraft Ltd Vibration absorbing systems
GB1468359A (en) * 1973-10-09 1977-03-23 Westland Aircraft Ltd Bifilar vibration dampers
US3988073A (en) * 1975-04-11 1976-10-26 United Technologies Corporation Spherical bifilar tuning pin bushing
US3988074A (en) * 1975-11-13 1976-10-26 United Technologies Corporation Anhedral bifilar
US4057363A (en) * 1975-11-20 1977-11-08 United Technologies Corporation Extended arm bifilar and method to eliminate second order vibration excitation
GB1528057A (en) * 1976-01-20 1978-10-11 Westland Aircraft Ltd Vibration absorbers
US4212588A (en) * 1978-05-11 1980-07-15 United Technologies Corporation Simplified rotor head fairing
US4213518A (en) * 1978-08-04 1980-07-22 United Technologies Corporation Fixed position pendular-type vibration absorber with linearization at fixed or variable frequencies
US4218187A (en) * 1978-08-04 1980-08-19 United Technologies Corporation Constant frequency bifilar vibration absorber
IL57943A (en) * 1978-08-04 1983-06-15 United Technologies Corp Vibration absorber of pendular construction particularly for helicopters
US4239455A (en) * 1978-09-11 1980-12-16 Textron, Inc. Blade-mounted centrifugal pendulum
US4239456A (en) * 1979-05-10 1980-12-16 Textron, Inc. Rotor blade out-of-plane centrifugal pendulums
US4470121A (en) * 1981-08-17 1984-09-04 United Technologies Corporation Multi-frequency vibration controller using fluid-filled cantilever beam for vibration excitation & absorption
US4739679A (en) * 1986-01-23 1988-04-26 Ford Motor Company Bifilar pendulum vibration damper for automotive installation
US5495924A (en) * 1994-07-13 1996-03-05 Quiescence Engineering Corp. Half-order centrifugal pendulum vibration absorber system
FR2733483B1 (en) * 1995-04-27 1997-07-04 Eurocopter France VIBRATION MITIGATION DEVICE FOR A HELICOPTER ROTOR
US5954480A (en) * 1997-08-28 1999-09-21 Sikorsky Aircraft Corporation Vibration isolator for rotorcraft
US5901616A (en) * 1997-09-15 1999-05-11 Sikorsky Aircraft Corporation Inertial mass for vibration isolators
US6883752B2 (en) * 2001-11-14 2005-04-26 Brp-Rotax Gmbh & Co. Kg. Vibration damper for aircraft engine
US7118328B2 (en) * 2004-03-12 2006-10-10 Sikorsky Aircraft Corporation Gearbox mounted force generator
US7722322B2 (en) * 2004-08-30 2010-05-25 Lord Corporation Computer system and program product for controlling vibrations
US8090482B2 (en) 2007-10-25 2012-01-03 Lord Corporation Distributed active vibration control systems and rotary wing aircraft with suppressed vibrations
CN101022994B (en) 2004-08-30 2012-07-04 洛德公司 Helicopter vibration control system and rotary force generator for canceling vibrations
US8162606B2 (en) * 2004-08-30 2012-04-24 Lord Corporation Helicopter hub mounted vibration control and circular force generation systems for canceling vibrations
US8435002B2 (en) * 2004-08-30 2013-05-07 Lord Corporation Helicopter vibration control system and rotating assembly rotary forces generators for canceling vibrations
US8267652B2 (en) * 2004-08-30 2012-09-18 Lord Corporation Helicopter hub mounted vibration control and circular force generation systems for canceling vibrations
DE112008003167B4 (en) 2007-11-29 2016-07-21 Schaeffler Technologies AG & Co. KG Power transmission device with a speed adaptive absorber and method for improving the damping behavior
FR2945789B1 (en) * 2009-05-20 2011-05-13 Eurocopter France DEVICE WITH DISTRIBUTED MASSES FOR REDUCING VIBRATIONS GENERATED BY A ROTOR OF SUSTENTATION OF A GIRAVION, AND HUB OF A ROTOR HAVING SUCH A DEVICE
FR2951698B1 (en) 2009-10-27 2012-03-30 Eurocopter France DEVICE FOR REDUCING THE VIBRATIONS GENERATED BY A ROTOR OF A GIRAVION, AND GIRAVION PROVIDED WITH SUCH A DEVICE
FR2959484B1 (en) 2010-04-30 2012-11-09 Eurocopter France DEVICE FOR REDUCING VIBRATIONS GENERATED BY A ROTOR OF SUSTENTATION OF A GIRAVION, AND HUB OF A ROTOR HAVING SUCH A DEVICE.
GB2482545B (en) * 2010-08-06 2017-05-03 Ge Aviat Systems Ltd Aircraft propellers with composite blades mounted to a single propeller hub
CN103874613B (en) * 2011-10-17 2016-11-23 丰田自动车株式会社 The control device of motor vehicle driven by mixed power
US10507920B2 (en) 2015-05-18 2019-12-17 Sikorsky Aircraft Corp. Systems and methods for lifting body vibration control
US10569870B2 (en) * 2016-11-18 2020-02-25 Textron Innovations Inc. Proprotor systems for tiltrotor aircraft
US10577089B2 (en) * 2017-05-03 2020-03-03 Sikorsky Aircraft Corporation Integrated bifilar system that absorbs vibrations in both vertical and in-plane directions
US12110117B2 (en) * 2021-08-23 2024-10-08 Goodrich Corporation Heated pendulum damper

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR773520A (en) * 1933-05-26 1934-11-21 Device to reduce torsional vibrations
US2280360A (en) * 1939-06-15 1942-04-21 Florence Z Walsh Garment
US2343421A (en) * 1942-07-31 1944-03-07 Fairbanks Morse & Co Torsional vibration damper
US2348941A (en) * 1942-12-05 1944-05-16 Packard Motor Car Co Vibration damping device
US2480946A (en) * 1943-09-02 1949-09-06 Gen Motors Corp Torsional vibration damper
DE1100498B (en) * 1958-04-02 1961-02-23 Leo Costa Dr Ing Device for damping the impact caused by the tip vortex of the propeller's wings
US3372758A (en) * 1967-02-15 1968-03-12 United Aircraft Corp Vibration absorber

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4550812A (en) * 1978-08-04 1985-11-05 United Technologies Corporation Fixed position, fixed frequency pendular-type vibration absorber with frequency linearization

Also Published As

Publication number Publication date
US3540809A (en) 1970-11-17
DE1940770C3 (en) 1973-01-04
DE1940770A1 (en) 1970-03-26
FR2018491B1 (en) 1974-03-15
FR2018491A1 (en) 1970-05-29
SE352586B (en) 1973-01-08

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PE20 Patent expired after termination of 20 years